Compressor stabilizer channel

Abstract

The present invention relates to a stabilizer channel (10), particularly for centrifugal or mixed-flow compressors, having an annular stabilizer chamber (12) surrounding a main flow path (13) in the suction region of a compressor wheel (21) and separated from the main flow path (13) by an annular bridge (14). The annular stabilizer channel (12) is connected to the main flow path (13) via a downstream flow inlet (15) and an upstream flow outlet (16). At least one separation element (T) is arranged in at least one of the flow inlet (15) and the flow outlet (16), so that the inflow flow into the annular stabilizer chamber (12) and / or the outflow flow from the annular stabilizer chamber (12) is divided transversely to the main flow direction (1) of the main flow path (13). Furthermore, at least one flow guide element (17) is arranged in at least one of the flow inlet (15) and the flow outlet (16). The invention further relates to a compressor, in particular a centrifugal compressor or a mixed-flow compressor, comprising a stabilizer channel according to the invention, and to a turbomachine, in particular a turbocharger, comprising such a compressor.

Description

[Technical Field]

[0001] The present invention relates to the field of compressors, particularly centrifugal and diagonal compressors. In particular, the present invention relates to a stabilizer channel at the compressor inlet for improving the map width and characteristic curve slope of a compressor stage. [Background technology]

[0002] Exhaust gas turbochargers are used to increase the power output of internal combustion engines, in particular reciprocating piston engines. In this connection, exhaust gas turbochargers usually comprise a centrifugal or mixed flow compressor and a radial or axial flow turbine.

[0003] The operating range of centrifugal and mixed-flow compressors is limited to smaller mass flow rates by surge limits / flow instabilities, and when the compressor is throttled, the incidence angle gradually deteriorates until the flows separate and surge occurs. The allowable incidence angle range, where the flows are still in contact, decreases with increasing flow Mach number; this means that stages with high pressure ratios and / or high suction capacities tend to have smaller map widths.

[0004] To stabilize the characteristic curve, a bypass in the form of an annular cavity in the compressor housing can be provided above the compressor wheel profile, parallel to the suction duct. This type of bypass is also known as a stabilizer chamber or recirculator. The use of a recirculator allows the mass flow at the compressor wheel inlet to be artificially increased near the surge limit. Part of the mass flow is diverted from the compressor wheel to a side chamber (bypass). This mass flow has a strong swirl component (swirl in the impeller rotation direction: entrained swirl). This entrained swirl reduces the compressor's work conversion and causes a shallower characteristic curve near the surge limit.

[0005] In applications with pressure pulsations (e.g., due to valve operation in supercharged internal combustion engines), a shallow characteristic curve near the surge limit can lead to unexpected surges. This creates a demand for providing a minimum pressure rise between the operating point on the operating speed characteristic and the surge limit. This demand is rarely met with high pressure ratios and conventional bypass / stabilizer channel stages due to the high work conversion and shallow work coefficient curve for mass flow at constant speed. Summary of the Invention [Problem to be solved by the invention]

[0006] The object of the present invention is to provide a stabilizer channel for a compressor, in particular a centrifugal or mixed-flow compressor, which is improved with respect to at least one of the drawbacks known from the prior art. It is also an object of the present invention to provide an improved compressor and an improved turbomachine, in particular an improved turbocharger. [Means for solving the problem]

[0007] To achieve the above object, there is provided a stabilizer channel for a compressor, in particular a centrifugal compressor or a mixed-flow compressor, as set forth in independent claim 1. Furthermore, there is provided a compressor having a stabilizer channel according to the embodiments described herein, and a turbomachine, in particular a turbocharger, having such a compressor.

[0008] Further aspects, advantages and features of the invention can be found in the dependent claims, the description and the drawings.

[0009] According to one aspect of the present invention, there is provided a stabilizer channel for a compressor, particularly a centrifugal compressor or a mixed-flow compressor. The stabilizer channel includes an annular stabilizer chamber surrounding a main flow path in the suction region of a compressor wheel. The annular stabilizer chamber is separated from the main flow path by an annular web. The annular stabilizer chamber is connected to the main flow path via a downstream flow inlet and an upstream flow outlet. At least one separation element is disposed in at least one of the downstream flow inlet and the upstream flow outlet, such that the inflow flow into the annular stabilizer chamber and / or the outflow flow from the annular stabilizer chamber are divided transversely to the main flow direction of the main flow path. Furthermore, at least one flow guide element is disposed in at least one of the downstream flow inlet and the upstream flow outlet.

[0010] Thus, a stabilizer channel is advantageously provided that can improve the map width and characteristic curve slope of a compressor stage. Specifically, flow splitting at the downstream flow inlet and / or upstream flow outlet, e.g., in combination with flow guidance by flow directing elements described herein, has the advantage that tip clearance vortices at the impeller (e.g., compressor wheel) can be better influenced by more uniform suction compared to the prior art. Appropriate placement of separation elements within the downstream flow inlet and / or upstream flow outlet can reduce the penetration depth of tip clearance vortices and favorably influence their direction, especially when additional flow directing elements are used. Improved stability and / or higher efficiency can be achieved with the embodiments described herein compared to conventional configurations that do not split the incoming flow into and / or the outgoing flow from the stabilizer chamber.

[0011] According to a second aspect of the present invention, there is provided a compressor, in particular a centrifugal compressor or a mixed-flow compressor, comprising a compressor wheel and a stabilizer channel according to one of the embodiments described herein. In particular, the compressor wheel comprises, in the region of the flow inlet to the stabilizer channel, a number N1 of compressor wheel blades and a number N2 of the at least one flow guiding elements, where N2≧1.5×N1.

[0012] It is therefore possible to advantageously provide a compressor with improved characteristic map width and characteristic curve gradient, in particular with reduced noise and vibration generation during operation.

[0013] A third aspect of the present invention relates to a turbomachine, in particular a turbocharger, having a compressor according to one of the embodiments described herein, which advantageously results in an improved turbocharger over the prior art.

[0014] The invention will now be described with reference to exemplary embodiments which are shown and from which further advantages and modifications can be obtained. [Brief explanation of the drawings]

[0015] [Figure 1] 1 shows a schematic diagram of a stabilizer channel according to the prior art. [Figure 2] 1 shows a schematic diagram of a stabilizer channel according to embodiments described herein. [Figure 3a] 10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein, the stabilizer channel being incorporated into an insert; [Figure 3b] 1 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein, the stabilizer channel being part of a compressor inner housing. [Figure 4] 10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein. [Figure 5]10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein. [Figure 6] 10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein. [Figure 7] 10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein. [Figure 8] 10 shows a schematic diagram of a stabilizer channel according to a further embodiment described herein. [Figure 9a] 10A-10C show schematic diagrams of configurations of flow guiding elements in a downstream inlet channel to generate a reverse swirl flow as the flow passes through the guiding elements. [Figure 9b] 10 shows a schematic diagram of a configuration of flow guiding elements in an upstream outlet channel to generate a counter-swirling flow while the flow passes through the guiding elements. [Figure 10a] 10A-10C show schematic diagrams of configurations of flow guiding elements in downstream inlet channels to reduce swirl flow as the flow passes through the guiding elements. [Figure 10b] 10A-10C show schematic diagrams of configurations of flow guiding elements in an upstream outlet channel to reduce swirl flow as the flow passes through the guiding elements. DETAILED DESCRIPTION OF THE INVENTION

[0016] Reference will now be made in detail to various embodiments, one or more examples of which are illustrated in the various figures. Each example is illustrative and should not be construed as limiting. For example, features illustrated or described as part of one embodiment may be used on or in combination with any other embodiment to yield a further embodiment. The present disclosure is intended to include such modifications and variations.

[0017] In the following description of the drawings, the same reference numerals refer to the same or similar components. Generally, only differences relating to individual embodiments are described. Unless otherwise specified, the description of a part or aspect in one embodiment may also relate to a corresponding part or aspect in another embodiment.

[0018] FIG. 1 shows a schematic diagram of a stabilizer channel 10 according to the prior art. In particular, FIG. 1 shows a cross section along the rotation axis 11 of a compressor wheel 21 through the housing of a centrifugal compressor of the kind used, for example, to compress air in exhaust gas turbochargers. A stabilizer chamber 12 is arranged in the compressor housing 5. The stabilizer chamber 12 is connected to a main flow path 13 via an inlet channel 3 and an outlet opening 4. The stabilizer chamber 12 is separated from the main flow path 13 by an annular web 14. A retaining rib 121 arranged in the stabilizer chamber 12 connects the annular web 14 to the compressor housing.

[0019] An embodiment of a stabilizer channel for a compressor according to the present disclosure will now be described with reference to Figures 2 to 10. The compressor may be a centrifugal compressor or a mixed flow compressor.

[0020] According to one embodiment, which can be combined with other embodiments described herein, the stabilizer channel 10 comprises an annular stabilizer chamber 12 surrounding the main flow path 13 in the suction region of the compressor wheel 21, as exemplarily shown in FIG. 2 . In other words, the stabilizer channel 10 is typically disposed at the compressor inlet. In this regard, it should be noted that in this disclosure, the term "stabilizer channel" should be understood to mean, in particular, a channel at the compressor inlet configured to improve the map width of the compressor stage. For example, the stabilizer channel 10 can be a recirculation channel.

[0021] The annular stabilizer chamber 12 is separated from the main flow path 13 by an annular web 14. The annular stabilizer chamber 12 is connected to the main flow path 13 via a downstream flow inlet 15 and an upstream flow outlet 16. The annular stabilizer chamber 12 may be of a rotationally symmetric design.

[0022] At least one separation element T is disposed at at least one of the flow inlet 15 and the flow outlet 16. Figure 2 shows an exemplary embodiment with a separation element T disposed at the flow inlet 15 to the annular stabilizer chamber 12. Figures 8a and 8b show an exemplary embodiment with a separation element T disposed at the flow outlet 16 from the annular stabilizer chamber 12.

[0023] The separation elements T are arranged so that the inflow flow to and / or the outflow flow from the annular stabilizer chamber 12 is divided transversely to the main flow direction 1 of the main flow channel 13. In other words, the separation elements T are configured and arranged so that the flow is divided. For example, at least one separation element T can be configured to divide the inflow flow to the stabilizer chamber 12 and arranged at the flow inlet 15. Alternatively or additionally, at least one separation element T can be configured to divide the outflow flow from the stabilizer chamber 12 and arranged at the flow outlet 16. Typically, the separation element is embodied in the form of a divider wall having a continuous dividing wall surface. Alternatively, the separation element, in particular the partition wall, can have one or more holes, so that the partition wall surface is partially interrupted.

[0024] 2, at least one flow guiding element 17 is disposed at at least one of the flow inlet 15 and the flow outlet 16. The at least one flow guiding element 17 may be in the form of, for example, a spiral. Typically, the at least one flow guiding element 17 is composed of a plurality of flow guiding elements, which are arranged circumferentially around the central axis 11 of the main flow channel 13. In particular, the plurality of flow guiding elements 17 may be arranged concentrically around the central axis 11 of the main flow channel 13.

[0025] In this disclosure, the terms "downstream" and "upstream" refer to the main flow in the main flow path at the suction area of ​​the compressor wheel. For better understanding, the direction of the main flow path 1 is marked on the figures. According to one embodiment, as shown in FIG. 2, the flow inlet 15 of the stabilizer chamber can be located downstream of the inlet edge 24 of the compressor wheel 21. The flow outlet 16 of the stabilizer chamber is typically located upstream of the inlet edge 24 of the compressor wheel 21.

[0026] According to one embodiment, which can be combined with other embodiments described herein, the stabilizer channel 10 is an integral part of the compressor housing, as exemplarily shown in Figure 2. Alternatively, the stabilizer channel 10 can be incorporated into an insert 22 that is attached to the suction area of ​​the compressor, as exemplarily shown in Figure 3a. According to another example, the stabilizer channel can be part of the compressor inner housing 20A, as exemplarily shown in Figure 3b, which shows a compressor 20 having a compressor inner housing 20A and a compressor outer housing 20B.

[0027] According to one embodiment, which can be combined with other embodiments described herein, as exemplarily shown in Figures 2 to 7, at least one separation element T is arranged at the flow inlet 15 so as to provide two or more downstream inlet channels 150. As can be seen from Figures 2 to 7, the two or more downstream inlet channels 150 are axially spaced apart.

[0028] For example, as exemplarily shown in FIGS. 4, 5a, 5b, and 7, at least one of the two or more downstream inlet channels 150 can be designed differently from the other inlet channel(s). Specifically, at least one of the two or more downstream inlet channels can differ from the other inlet channel(s) in terms of channel width and / or channel shape. For example, at least one inlet channel can have a smaller inlet channel width than the other inlet channel(s) of the two or more downstream inlet channels. By way of illustration, FIG. 5a shows an exemplary embodiment having three inlet channels 151, 152, 153 with different channel widths w1, w2, and w3. Alternatively or additionally, at least one inlet channel can have a radial cross-sectional taper. By way of illustration, in FIG. 4, the second inlet channel 152 is shown as having a cross-sectional taper 173. Note that the two or more downstream inlet channels 150 can also have the same configuration.

[0029] In the present disclosure, the term "inlet channel" should be understood to mean a channel that functions as a flow inlet channel to the stabilizer chamber. Typically, the inlet channel 150 described herein is composed of an inlet opening 15A on the main flow path side and an outlet opening 15B on the stabilizer chamber side, as exemplarily shown in Figures 5b and 7.

[0030] According to one embodiment, which can be combined with other embodiments described herein, at least one flow directing element 17 is disposed in each of at least two of the two or more downstream inlet channels 150. For example, the at least one flow directing element 17 can be designed differently, particularly in terms of number and / or shape, in one of the two or more downstream inlet channels 150 from another of the two or more downstream inlet channels 150. By way of illustration, FIG. 5 a shows a first group of flow directing elements 171 in the first inlet channel 151 and a second group of flow directing elements 172 in the second inlet channel 152 and the third inlet channel 153.

[0031] According to one embodiment, which can be combined with other embodiments described herein, the two or more downstream inlet channels 150 extend substantially radially. In the present disclosure, the term "substantially radially" should be understood to mean an angular range of -45°≦α≦45° or less, particularly -25°≦α≦25° or less, relative to the radial direction r. As exemplarily shown, the radial direction r extends perpendicular to the central axis 11. According to one example, "substantially radially" should be understood to mean an angular range of ±10° or less relative to the radial direction r. For further understanding, an inlet channel 150 inclined by an angle α, which falls within the above definition of "substantially radially," is exemplarily shown in FIG. 6. The angle α is in the xr plane.

[0032] According to one embodiment, which can be combined with other embodiments described herein, the two or more downstream inlet channels 150 can be comprised of a substantially radially extending portion 15C and a substantially axially extending portion 15D, as exemplarily shown in Figure 7. A transition region 15F, which is typically curved, exists between the substantially radially extending portion 15C and the substantially axially extending portion 15D.

[0033] According to one embodiment, which can be combined with other embodiments described herein, two or more downstream inlet channels 150 are disposed between an upstream portion 141 of the circumferential web 14 and a downstream portion 142 of the circumferential web 14, as exemplarily shown in FIG. 2. The upstream portion 141 of the circumferential web 14 can have a first extension 18 extending substantially radially, as exemplarily shown in FIG. 4. The downstream portion 142 of the circumferential web 14 can include a second extension 19A extending substantially radially. Alternatively or additionally, the downstream portion 142 of the circumferential web 14 can include a second extension 19B extending substantially axially, as exemplarily shown in FIG. 7.

[0034] According to one embodiment, which can be combined with other embodiments described herein, at least one flow guiding element 17 is arranged in at least one outlet region 15E of the inlet channel 150 on either one or both of the stabilizer chambers, as exemplarily shown in FIG. 5b.

[0035] The outlet region of the inlet channel 150 described herein should be understood to mean the region of the inlet channel 150 located on the same side as the outlet opening 15B on the stabilizer chamber side. For example, the outlet region can extend over half the inlet channel length L or less. For better understanding, the outlet region 15E of the inlet channel 15 is exemplarily shown in FIG. 5b. The placement of at least one flow guiding element 17 in the outlet region of the inlet channel can have a favorable effect on flow losses and blade vibration excitation.

[0036] According to one embodiment, which can be combined with other embodiments described herein, at least one separation element T is disposed at the upstream flow outlet 16. In particular, the at least one separation element T is disposed at the upstream flow outlet 16 so as to provide two or more upstream outlet channels 160.

[0037] As shown in Figures 8a and 8b, the two or more upstream outlet channels 160 are axially spaced apart. Furthermore, at least one outlet channel of the two or more upstream outlet channels 160 can be designed differently from the other outlet channel(s). In particular, at least one outlet channel of the two or more upstream outlet channels 160 differs from the other outlet channel(s) in terms of channel width and / or channel shape. For example, the at least one outlet channel can have a smaller outlet channel width than the other outlet channel(s) of the two or more upstream outlet channels. It should be noted that the two or more upstream outlet channels 160 can also be identically configured.

[0038] According to one embodiment, which can be combined with other embodiments described herein, as exemplarily shown in Figure 8b, at least one flow directing element 17 is arranged in each of at least two of the two or more upstream outlet channels 160. For example, the at least one flow directing element 17 can be designed to be different in one of the two or more upstream outlet channels 160 from another of the two or more upstream outlet channels 160, particularly in terms of number and / or shape.

[0039] According to one embodiment, which can be combined with other embodiments described herein, the two or more upstream outlet channels 160 extend substantially radially.

[0040] According to one embodiment, which can be combined with other embodiments described herein, as exemplarily shown in Figures 8a and 8b, two or more upstream outlet channels 160 are disposed between the main flowpath wall 131 and the upstream portion 141 of the annular web 14. In particular, the two or more upstream outlet channels 160 are disposed between the substantially radially extending third extension 18a of the upstream portion 141 of the annular web 14 and the substantially radially extending extension 132 of the main flowpath wall 131.

[0041] According to one embodiment, which can be combined with other embodiments described herein, at least one flow guiding element 17 is arranged in the inlet region 16E of at least one of two or more outlet channels 160 of the stabilizer chamber, as exemplarily shown in FIG. 8b.

[0042] The inlet region 16E of the outlet channel 160 described herein should be understood to mean the region of the outlet channel 160 that is located on the same side as the stabilizer chamber 12. The inlet region 16E can, for example, extend over half the length of the outlet channel or less.

[0043] According to one embodiment, which can be combined with other embodiments described herein, the at least one flow directing element 17 is designed and arranged to provide a deflection grid along which the flow can occur, which can be a deflection grid along which the flow can occur substantially radially.

[0044] According to an alternative embodiment, which can be combined with other embodiments described herein, the at least one flow guiding element 17 is designed and arranged to provide a deflection grid in which the flow can be generated substantially axially, as exemplarily shown in FIG. 7 . In the present disclosure, the term “substantially axially” should be understood to mean an angular range of ±45° or less, particularly ±25° or less, relative to the axial direction x. As exemplarily shown in FIG. 7 , the axial direction x extends along the central axis 11. According to one embodiment, “substantially axially” should be understood to mean an angular range of ±10° or less relative to the axial direction x. A deflection grid in which the flow can be generated substantially axially can be provided, for example, by the configuration of the inlet channel 150 of the stabilizer chamber and the arrangement of the at least one flow guiding element 17 according to FIG. 7 .

[0045] According to one embodiment, which can be combined with other embodiments described herein, at least one of the at least one flow guiding element 17 is embodied as a separate component.

[0046] According to one embodiment, which can be combined with other embodiments described herein, at least one of the at least one flow directing element 17 is integrally formed (in one piece) with at least one adjacent component. As can be seen in the figures, the adjacent components to the at least one flow directing element 17 are the separation element T, in particular the upstream portion 141 of the annular web 14 having the first extension 18 and / or the third extension 18A, in particular the downstream portion 142 of the annular web 14 having the second extension 19A or 19B, and the main channel wall 131, in particular having the extension 132.

[0047] According to one embodiment, which can be combined with other embodiments described herein, at least one of the plurality of flow guiding elements 17, in particular at least half or all, is formed from a Curtis-type blade profile. In particular, at least one of the plurality of flow guiding elements 17, in particular at least half or all, can be a prismatic Curtis-type blade. Typically, the flow guiding elements 17 are designed as radially deflecting blades. Embodiments of the flow guiding elements from a Curtis-type blade profile, in particular flow guiding elements in the form of prismatic Curtis-type blades, have the advantage that they can be relatively thick, which allows for better coupling of the flow guiding elements 17 to adjacent components, for example by means of a threaded joint as defined herein or other suitable types of joints.

[0048] According to one embodiment, which can be combined with other embodiments described herein, the downstream portion 142 of the annular web 14 has a centering shoulder, in particular a cylindrical or conical centering shoulder. Alternatively or additionally, the separation element T can have a centering shoulder, in particular a cylindrical or conical centering shoulder. Alternatively or additionally, the upstream portion 141 of the annular web 14 can have a centering shoulder, in particular a cylindrical or conical centering shoulder.

[0049] According to one embodiment, which can be combined with other embodiments described herein, the upstream portion 141 of the annular web 14 and the downstream portion 142 of the annular web 14 are connected via at least one flow guiding element 17, in particular via a plurality of flow guiding elements 17 and a separation element T, for example by a threaded or pinned joint. The threaded or pinned joint can extend through the at least one flow guiding element 17, in particular through one or more flow guiding elements 17 and a separation element T. It should be noted that the threaded or pinned joint can also be embodied in some other way, i.e., not extending through the at least one flow guiding element 17 or the separation element T. Alternatively or additionally, other types of connections, such as shrinking or clamping, can be used.

[0050] According to one embodiment, which can be combined with other embodiments described herein, the at least one flow guiding element 17 has a centering seat that is designed to circumferentially, in particular concentrically, position the at least one flow guiding element 17 in the downstream flow inlet 15, in particular in one or more downstream inlet channels, around the central axis 11 of the main flow channel 13. Alternatively or additionally, the at least one flow guiding element 17 has a centering seat that is designed to circumferentially, in particular concentrically, position the at least one flow guiding element 17 in the upstream flow outlet 16, in particular in one or more upstream outlet channels, around the central axis 11 of the main flow channel 13. The centering seat can be implemented, for example, by one or more centering elements, one or more centering pins, or a centering edge on the component to be centered.

[0051] According to one embodiment, which can be combined with other embodiments described herein, at least one flow guiding element 17 has an inlet end 17a and an outlet end 17b. The downstream end of the at least one flow guiding element 17 can be inclined circumferentially relative to the inlet end 17A of the at least one flow guiding element 17, thereby ensuring reduced swirl or the generation of a counter-swirl during flow through. By way of example, FIGS. 9a and 10a show cross sections of a downstream inlet channel 150 having multiple flow guiding elements 17, depicting the direction of rotation 2 of the compressor wheel that induces swirling flow. FIG. 9a shows a configuration of the flow guiding elements 17 that can generate a counter-swirl during flow through, as exemplarily indicated by the arrows between the inlet end 17a and the outlet end 17b. FIG. 9b shows a schematic diagram of a configuration of the flow guiding elements 17 in an upstream outlet channel 160 for generating a counter-swirl of the flow during flow passing through the guiding elements. Figure 10a shows a configuration of flow directing elements 17 in a downstream inlet channel 150 that can reduce swirl during flow through. Figure 10b shows a schematic diagram of a configuration of flow directing elements 17 in an upstream outlet channel 160 to reduce swirl flow as the flow passes through the directing elements.

[0052] It is further noted that flow directing element 17 can be embodied to be flush with an inlet opening located on the main flow path side of inlet channel 150 described herein and / or can be embodied to be flush with an outlet opening located on the stabilizer chamber side of inlet channel 150 described herein. Alternatively, flow directing element 17 can be spaced apart from an inlet opening located on the main flow path side of inlet channel 150 described herein and / or from an outlet opening located on the stabilizer chamber side of inlet channel 150 described herein.

[0053] In a similar manner, flow directing element 17 can be embodied to be flush with an outlet opening located on the main flow path side of outlet channel 160 described herein and / or flush with an inlet opening located on the stabilizer chamber side of outlet channel 160 described herein. Alternatively, flow directing element 17 can be spaced apart from an outlet opening located on the main flow path side of outlet channel 160 described herein and / or from an inlet opening located on the stabilizer chamber side of outlet channel 160 described herein.

[0054] According to one embodiment, which can be combined with other embodiments described herein, the annular stabilizer chamber 12 does not have blades. In other words, blades, in particular flow guide blades, are not arranged in the annular stabilizer chamber 12. In particular, the annular stabilizer chamber 12 can also be strut-free. In other words, the annular stabilizer chamber 12 can be blade-free and strut-free, and therefore the annular stabilizer chamber 12 is also free of flow guide blades and struts.

[0055] According to a second aspect of the present disclosure, a compressor 20, in particular a centrifugal or mixed-flow compressor, is provided, comprising a compressor wheel 21 according to one of the embodiments described herein and a stabilizer channel 10. According to one embodiment, which can be combined with other embodiments described herein, the compressor wheel 21 comprises, in the region of the flow inlet 15, a number N1 of compressor wheel blades 23 and a number N2 of guiding elements of the at least one flow guiding element 17, where N2≧1.5×N1.

[0056] It is therefore advantageously possible to provide a compressor with improved characteristic map width and characteristic curve gradient, in particular with reduced noise and vibration generation during operation of the compressor.

[0057] A third aspect of the present invention relates to a turbomachine, in particular a turbocharger, having a compressor according to one of the embodiments described herein, resulting in an advantageously improved turbomachine, in particular a turbocharger, over the prior art. [Explanation of symbols]

[0058] 1 Main flow direction 2 Compressor wheel rotation direction 3 Prior art inlet channels 4 Prior art outlet opening 5 Compressor housing 10 Stabilizer Channel 11 Central shaft / Compressor wheel rotation axis 12 Annular stabilizer chamber 121 Strut 13 Main channel 131 Main channel wall 132 Main channel wall extension 14 Circular Web 141 Upstream portion of circular web 142 downstream portion of the circular web 15 downstream flow inlet of stabilizer chamber 150 Two or more downstream inlet channels 151 First Entrance Channel 152 Second Entrance Channel 153 Third Entrance Channel 15A Inlet opening located on the main flow path side of two or more inlet channels 15B Outlet openings located on the stabilizer chamber side of two or more inlet channels 15C Substantially radially extending portions of two or more inlet channels 15D A substantially axially extending portion of two or more inlet channels 15E Outlet area of ​​two or more inlet channels 15F Transition region of two or more inlet channels 16. Upstream flow outlet of stabilizer chamber 16E Inlet area of ​​two or more outlet channels 160 Two or more upstream outlet channels 17 At least one flow guiding element(s) 171 First group of flow guide elements 172 Second group of flow guide elements 173 Cross-sectional tapered 17A Inlet end of flow guide element 17B Outlet end of flow guide element 18 first extension extending substantially radially 18A: a third extension extending substantially radially 19A second extension extending substantially radially 19B a second extension extending substantially axially 20 Compressor 20A Compressor inner housing 20B Compressor outer housing 21 Compressor wheel 22 Insert 23 Compressor wheel blade 24 Compressor wheel inlet edge T separation element r radial direction x-axis direction L is the length of two or more inlet channels of the stabilizer chamber w1: Channel width of the first inlet channel w2 Second entrance channel width w3 Channel width of the third inlet channel α Angle in the xr plane to explain "substantially radial"

Claims

1. 1. A stabilizer channel (10) for a compressor, comprising an annular stabilizer chamber (12) surrounding a main flow path (13) in the suction region of a compressor wheel (21) and bounded relative to the main flow path (13) by an annular web (14), The annular stabilizer chamber (12) is connected to the main flow path (13) via a downstream flow inlet (15) and an upstream flow outlet (16); at least one separation element (T) is arranged at at least one of the downstream flow inlet (15) and the upstream flow outlet (16), so that at least one of the inflow flow to the annular stabilizer chamber (12) and the outflow flow from the annular stabilizer chamber (12) is divided transversely to a main flow direction (1) of the main flow path (13); at least one flow directing element (17) is arranged at at least one of the downstream flow inlet (15) and the upstream flow outlet (16); said at least one separation element (T) is arranged at said downstream flow inlet (15) so as to provide two or more downstream inlet channels (150); the two or more downstream inlet channels (150) are disposed between the upstream portion (141) of the circumferential web (14) and the downstream portion (142) of the circumferential web (14); the upstream portion (141) of the annular web (14) comprises a first radially extending extension (18); the downstream portion (142) of the annular web (14) comprises a second radially extending extension (19A); and the downstream portion (142) of the annular web (14) comprises a second axially extending extension (19B); At least one of the following applies: Stabilizer channel (10).

2. At least one inlet channel of the two or more downstream inlet channels (150) is of a different design with respect to at least one of a channel width and a channel shape. The stabilizer channel (10) of claim 1.

3. the at least one separation element (T) is arranged at the downstream flow inlet (15) to provide the two or more downstream inlet channels (150), and the at least one flow directing element (17) is arranged in each of at least two of the two or more downstream inlet channels (150); A stabilizer channel (10) according to claim 1 or 2.

4. the two or more downstream inlet channels (150) extend radially, or the two or more downstream inlet channels (150) comprise a radially extending portion (15C) and an axially extending portion (15D); A stabilizer channel (10) according to claim 2 or 3.

5. the at least one flow guiding element (17) is arranged in an outlet region (15E) of at least one of the two or more inlet channels of the stabilizer chamber; A stabilizer channel (10) according to any one of claims 2 to 4.

6. the at least one separation element (T) is arranged at the upstream flow outlet (16) so as to provide the two or more upstream outlet channels (160); A stabilizer channel (10) according to any one of claims 1 to 5.

7. the at least one flow directing element (17) is disposed in each of at least two of the two or more upstream outlet channels (160); The stabilizer channel (10) according to claim 6.

8. the two or more upstream outlet channels (160) extend radially; the two or more upstream outlet channels (160) are disposed between the main flow wall (131) and the upstream portion (141) of the annular web (14); and the at least one flow guiding element (17) is arranged in an inlet region (16E) of at least one of the two or more outlet channels (160) of the stabilizer chamber; At least one of the following applies: A stabilizer channel (10) according to claim 6 or 7.

9. said at least one flow guiding element (17) being designed and arranged to provide a deflection grid on which a flow can be generated; at least one of said at least one flow directing element (17) is embodied as a separate component, and at least one of said at least one flow directing element (17) is integrally formed with at least one adjacent component; At least one of the following applies: The stabilizer channel according to any one of claims 1 to 8.

10. the at least one flow guiding element (17) has a centering seat designed to position the at least one flow guiding element (17) circumferentially around the central axis (11) of the main flow channel (13) in the downstream flow inlet (15) and / or in the upstream flow outlet (16). The stabilizer channel according to any one of claims 1 to 9.

11. the at least one flow guiding element (17) has an inlet end (17A) and an outlet end (17B), the outlet end (17B) being inclined circumferentially relative to the inlet end (17A), thereby ensuring at least one of reduced swirl and counter-swirl during throughflow. The stabilizer channel according to any one of claims 1 to 10.

12. A compressor (20) comprising a compressor wheel (21) and a stabilizer channel (10) according to any one of claims 1 to 11.

13. A turbomachine comprising a compressor (20) according to claim 12.

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